Turbomachine combustor including a combustor sleeve baffle

ABSTRACT

A turbomachine combustor includes a combustor body extending from a head end to a discharge end. The combustor body includes a combustor liner defining a combustion chamber. A combustor sleeve surrounds the combustor liner. The combustor sleeve is spaced from the combustor liner forming a passage. The combustor sleeve includes at least one opening. A baffle is arranged in the passage. The baffle includes a curvilinear surface extending from the combustor sleeve across the at least one opening toward the head end of the combustor body. The baffle is configured and disposed to compress a fluid flow passing through the passage toward the head end.

BACKGROUND OF THE INVENTION

The subject matter disclosed herein relates to the art of turbomachinesand, more particularly, to a turbomachine combustor including acombustor sleeve baffle.

Turbomachines include a compressor portion linked to a turbine portionthrough a common compressor/turbine shaft and a combustor assembly. Aninlet airflow is passed through an air intake toward the compressorportion. In the compressor portion, the inlet airflow is compressedthrough a number of sequential stages toward the combustor assembly. Inthe combustor assembly, the compressed airflow mixes with a fuel to forma combustible mixture. The combustible mixture is combusted in thecombustor assembly to form hot gases. The hot gases are guided along ahot gas path of the turbine portion through a transition piece. The hotgases expand along a hot gas path through a number of turbine stagesacting upon turbine bucket airfoils mounted on wheels to create workthat is output, for example, to power a generator. A portion of thecompressed air is passed through various components of the turbomachinefor cooling purposes. In some case, air for cooling is passed through acombustor sleeve that surrounds the combustor. The air for cooling mayenter the combustor as part of the combustible mixture.

BRIEF DESCRIPTION OF THE INVENTION

According to an aspect of an exemplary embodiment, a turbomachinecombustor includes a combustor body extending from a head end to adischarge end. The combustor body includes a combustor liner defining acombustion chamber. A combustor sleeve surrounds the combustor liner.The combustor sleeve is spaced from the combustor liner forming apassage. The combustor sleeve includes at least one opening. A baffle isarranged in the passage. The baffle includes a curvilinear surfaceextending from the combustor sleeve across the at least one openingtoward the head end of the combustor body. The baffle is configured anddisposed to compress a fluid flow passing through the passage toward thehead end.

According to another aspect of an exemplary embodiment, a turbomachineincludes a compressor portion, a turbine portion operatively connectedto the compressor portion, and a combustor assembly fluidicallyconnected to the compressor portion and the turbine portion. Thecombustor assembly includes at least one combustor having a combustorbody extending from a head end to a discharge end. The combustor bodyincludes a combustor liner defining a combustion chamber. A combustorsleeve surrounds the combustor liner. The combustor sleeve is spacedfrom the combustor liner forming a passage. The combustor sleeveincludes at least one opening. A baffle is arranged in the passage. Thebaffle includes a curvilinear surface extending from the combustorsleeve across the at least one opening toward the head end of thecombustor body. The baffle is configured and disposed to compress afluid flow passing through the passage toward the head end.

According to yet another aspect of an exemplary embodiment, a method ofpassing air through a combustor includes a passage defined between acombustor liner and a combustor sleeve including guiding a first airflowthrough the passage toward a head end of the combustor, passing thefirst airflow over a baffle, compressing the first airflow between thebaffle and the combustor liner, introducing a second airflow into thefirst airflow downstream of the baffle, and merging the first airflowand the second airflow creating a substantially turbulent free airflow.

These and other advantages and features will become more apparent fromthe following description taken in conjunction with the drawings.

BRIEF DESCRIPTION OF DRAWINGS

The subject matter, which is regarded as the invention, is particularlypointed out and distinctly claimed in the claims at the conclusion ofthe specification. The foregoing and other features, and advantages ofthe invention are apparent from the following detailed description takenin conjunction with the accompanying drawings in which:

FIG. 1 is a schematic representation of a turbomachine system includinga turbomachine having a combustor provided with a combustor sleevebaffle, in accordance with an exemplary embodiment;

FIG. 2 is a cross-sectional view of the combustor of FIG. 1;

FIG. 3 is a cross-sectional view of a portion of the combustor of FIG.2;

FIG. 4 is a cross-sectional view of the baffle of FIG. 1;

FIG. 5 is a cross-sectional view of the baffle of FIG. 4 rotatedcircumferentially illustrating holes an a curvilinear surface of thebaffle;

FIG. 6 is a partial perspective view of the baffle of FIG. 1; and

FIG. 7 is a cross-sectional view of the baffle, in accordance withanother aspect of an exemplary embodiment.

The detailed description explains embodiments of the invention, togetherwith advantages and features, by way of example with reference to thedrawings.

DETAILED DESCRIPTION OF THE INVENTION

With reference to FIGS. 1-4, a turbomachine system, in accordance withan exemplary embodiment, is indicated generally at 2, in FIG. 1.Turbomachine system 2 includes a turbomachine 3 having a compressorportion 4 operatively connected to a turbine portion 6 through a shaft8. Compressor portion 4 is fluidically connected to turbine portion 6through a combustor assembly 10 having at least one combustor 14. In theexemplary embodiment shown, turbomachine system 2 includes a drivenload/component 20 operatively connected to turbomachine 3. Drivencomponent 20 may take on a variety of forms including generators, pumps,and the load. Driven load may also take the form of a mode oftransportation driven by turbomachine 3. Turbomachine system 2 is alsoshown to include an air intake system 24 fluidically connected tocompressor portion 4.

Air enters air inlet system 24 and flows to compressor portion 4. Theair is compressed and passed to combustor assembly 10. A portion of theair is passed into turbine portion 6 for cooling. In combustor assembly10 the air is mixed with a fuel and or diluents to form a combustiblemixture. The combustible mixture is combusted forming hot gases thatpass from combustor assembly 10 to turbine portion 6. The hot gasesexpand through turbine portion 6 which converts thermal energy from thehot gases into mechanical energy that drives driven component 20. Thehot gases pass from turbine portion 6 to an exhaust system (not shown).

As best shown in FIGS. 2-3, combustor 14 includes a combustor body 34having a head end 36 and a discharge end 38 that is coupled to turbineportion 6 via a transition piece 42. Head end 36 houses a plurality ofnozzles 46. Combustor 14 also includes a combustor liner 50 arrangedwithin combustor body 34. Combustor liner 50 defines a combustionchamber 54. The combustible mixture is delivered into combustion chamber54 and combusted to form the hot gases delivered to turbine portion 6via transition piece 42. Combustor 14 also includes a combustor sleeve60 that circumscribes combustor liner 50. Combustor sleeve 60 is spacedfrom combustor liner 50 forming a passage 64. Passage 64 delivers anairflow from compressor portion 4 along combustor liner 50 toward headend 36 of combustor 14. A plurality of openings, one of which is shownat 68, extend through, and circumferentially about, combustor sleeve 60.As will be detailed more fully below, openings 68 deliver an airflowinto passage 64.

In accordance with an exemplary embodiment, combustor 14 includes abaffle 80 arranged in passage 64. Baffle 80 is arranged downstream fromany obstacles that may be present in passage 64. With this arrangement,air passing over baffle 80 has a substantially unobstructed flow path tohead end 36. As shown in FIG. 4, baffle 80 extends from a first end 83coupled to combustor sleeve 60 to a second, cantilevered end 84 througha curvilinear surface 86. Curvilinear surface 86 extends across openings68 and converges toward combustor liner 50. Air flowing through passage64 downstream of baffle 80 may be turbulent and circumferentially andradially non-uniform as a result of interaction with various componentssuch as injectors, cross-fire tubes, spark plugs, and the like such asshown at 88. The air reaches baffle 80 and is compressed betweencombustor liner 50 and curvilinear surface 86 reducing turbulence and/orreducing recirculation thereby enhancing circumferential uniformity.Additional air enters passage 64 through openings 68 and mixes with theair flowing across baffle 80. In accordance with an aspect of anexemplary embodiment, about 15% to about 30% of an overall airflowpassing through passage 64 downstream of baffle 80 enters throughopenings 68. The addition of air through openings 68 further reducesturbulence in the airflow passing to head end 36. Reducing turbulence inthe airflow passing to head end 36 enhances performance of combustor 14.

The reduction of turbulence in passage 64 resulting from compressing theair between combustion liner 50 and curvilinear surface 86 also improvesheat transfer from a hot side of the combustion liner 50 to air passingover the combustion liner 50 thereby prolonging an overall service lifeand reliability of combustor assembly 10. Performance improvements mayalso be realized by a reduction in pressure losses and by a reduction ofNOx emissions. More specifically, improving uniformity will lead to eachnozzle 46 receiving a substantially identical (by volume) air flow andthus create a more uniform air/flow mixture for combustion. Uniformityof the air/fuel mixtures leads to more complete combustion and improvedflameholding resulting in a reduction in emissions such as NOx.

In accordance with an aspect of an exemplary embodiment illustrated inFIG. 5, baffle 80 includes an opening 90 shown in the form of holes, twoof which are shown at 93 and 94, formed in curvilinear surface 86. Holes93 and 94 may be formed in curvilinear surface 86 between adjacent onesof openings 68. The incorporation of holes 93 and 94 enables additionalair to flow through baffle 80 in areas in which openings 68 may not bepresent. In accordance with another aspect of an exemplary embodimentillustrated in FIG. 6, baffle 80 is shown to include an opening 98.Opening 98 takes the form of an interruption or discontinuity 100 inbaffle 80. In a manner similar to that discussed above, opening 98enables additional air to flow through baffle 80 in areas in whichopenings 68 may not be present.

At this point it should be understood that the exemplary embodimentsdescribe a baffle arranged in an annular passage of a reverse flowcombustor. The baffle conditions a turbulent airflow passing along thecombustor toward the head end. More specifically, the baffle compressesthe airflow against the combustor liner to reduce air recirculationleading to enhanced flow uniformity. In this manner, the exemplaryembodiments reduce impingement pressure losses for air coming throughopenings in the baffle to enhance combustion properties of thecombustor. It should also be understood that baffle 80 may include adivergent portion 160 that may further enhance flow uniformity inpassage 64, as shown in FIG. 7. Divergent portion 160 may diverge fromsecond end 84 at an angle of less than 5 degrees. Of course the angle ofdivergent portion 160 may also be greater than 5 degrees.

While the invention has been described in detail in connection with onlya limited number of embodiments, it should be readily understood thatthe invention is not limited to such disclosed embodiments. Rather, theinvention can be modified to incorporate any number of variations,alterations, substitutions or equivalent arrangements not heretoforedescribed, but which are commensurate with the spirit and scope of theinvention. Additionally, while various embodiments of the invention havebeen described, it is to be understood that aspects of the invention mayinclude only some of the described embodiments. Accordingly, theinvention is not to be seen as limited by the foregoing description, butis only limited by the scope of the appended claims.

What is claimed is:
 1. A turbomachine combustor comprising: a combustorbody extending from a head end to a discharge end, the combustor bodyincluding a combustor liner defining a combustion chamber; a combustorsleeve surrounding the combustor liner, the combustor sleeve beingspaced from the combustor liner forming a passage, the combustor sleeveincluding at least one opening; and a baffle arranged in the passage,the baffle including a curvilinear surface extending from the combustorsleeve across the at least one opening toward the head end of thecombustor body, the baffle being configured and disposed to compress afluid flow passing through the passage toward the head end.
 2. Theturbomachine combustor according to claim 1, wherein the at least oneopening comprises a plurality of openings extending circumferentiallyabout the combustor sleeve.
 3. The turbomachine combustor according toclaim 2, wherein the baffle includes an opening arranged betweenadjacent ones of the plurality of openings.
 4. The turbomachinecombustor according to claim 3, wherein the opening includes at leastone hole formed in the curvilinear surface.
 5. The turbomachinecombustor according to claim 1, wherein the baffle extends from a firstend to a second, cantilevered end through the curvilinear surface, thesecond end includes a divergent portion.
 6. The turbomachine combustoraccording to claim 5, wherein the divergent portion diverges from thesecond end at an angle of less than 5 degrees.
 7. The turbomachinecombustor according to claim 1, wherein the passage is substantiallyunobstructed downstream of the baffle.
 8. A turbomachine comprising: acompressor portion; a turbine portion operatively connected to thecompressor portion; and a combustor assembly fluidically connected tothe compressor portion and the turbine portion, the combustor assemblyincluding at least one combustor, the at least one combustor including:a combustor body extending from a head end to a discharge end, thecombustor body including a combustor liner defining a combustionchamber; a combustor sleeve surrounding the combustor liner, thecombustor sleeve being spaced from the combustor liner forming apassage, the combustor sleeve including at least one opening; and abaffle arranged in the passage, the baffle including a curvilinearsurface extending from the combustor sleeve across the at least oneopening toward the head end of the combustor body, the baffle beingconfigured and disposed to compress a fluid flow passing through thepassage toward the head end.
 9. The turbomachine according to claim 8,wherein the at least one opening comprises a plurality of openingsextending circumferentially about the combustor sleeve.
 10. Theturbomachine according to claim 9, wherein the baffle includes anopening arranged between adjacent ones of the plurality of openings. 11.The turbomachine according to claim 10, wherein the opening includes atleast one hole formed in the curvilinear surface.
 12. The turbomachineaccording to claim 8, wherein the baffle extends from a first end to asecond, cantilevered end through the curvilinear surface, the second endincludes a divergent portion.
 13. The turbomachine according to claim 8,wherein the passage is substantially unobstructed downstream of thebaffle.
 14. A method of passing air through a combustor including apassage defined between a combustor liner and a combustor sleeve, themethod comprising: guiding a first airflow through the passage toward ahead end of the combustor; passing the first airflow over a baffle;compressing the first airflow between the baffle and the combustorliner; introducing a second airflow into the first airflow downstream ofthe baffle; and merging the first airflow and the second airflowcreating a substantially turbulent free airflow.
 15. The method of claim14, further comprising: passing a portion of the first airflow throughthe baffle.
 16. The method of claim 15, wherein passing the portion ofthe first airflow through the baffle includes passing the portion of thefirst airflow through openings formed in the baffle.
 17. The method ofclaim 15, wherein passing the portion of the first airflow through thebaffle includes passing the portion of the first airflow through aninterruption in the baffle.
 18. The method of claim 14, furthercomprising: passing the substantially turbulent free airflow toward thehead end of the combustor through an unobstructed portion of thepassage.
 19. The method of claim 14, wherein compressing the firstairflow includes passing the first airflow over a curvilinear surface ofthe baffle.
 20. The method of claim 14, further comprising: passing thesecond airflow over a divergent portion of the baffle.
 21. The method ofclaim 14, wherein creating the substantially turbulent free airflowenhances heat transfer from the combustion liner.
 22. The method ofclaim 14, wherein creating the substantially turbulent free airflowenhances circumferential uniformity of the airflow.
 23. The method ofclaim 14, wherein creating the substantially turbulent free airflowreduces impingement pressure losses.